Effects of wing flexibility on aerodynamic performance of an aircraft model

作     者：Qinfeng GUO Xi HE Zhuo WANG Jinjun WANG Qinfeng GUO;Xi HE;Zhuo WANG;Jinjun WANG

作者机构：Key Laboratory of Fluid MechanicsMinistry of EducationBeihang UniversityBeijing 100083China 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2021年第34卷第9期

页      面：133-142页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0802[工学-机械工程] 0825[工学-航空宇航科学与技术] 0801[工学-力学（可授工学、理学学位）] 

基　　金：supported by the National Natural Science Foundation of China(Nos.11761131009 and 11721202) 

主　　题：Aerodynamic forces Flexible wings Flow field Fluid structure interaction Wing tunnel tests 

摘      要：The low-speed wind tunnel experiment is carried out on a simplified aircraft model to explore the influence of wing flexibility on the aircraft aerodynamic *** investigation involves the measurements of force,membrane deformation and velocity field at Reynolds number of 5.4×10^(4)-1.1×10^(5).In the lift curves,two peaks are *** first peak,corresponding to the stall,is sensitive to the wing flexibility much more than the second peak,which nearly keeps *** the optimal case,in comparison with the rigid wing model,the delayed stall of nearly5°is achieved,and the relative lift increment is about 90%.It is revealed that the lift enhanced region corresponds to the larger deformation and stronger vibration,which leads to stronger flow mixing near the flexible wing ***,the leading-edge separation is suppressed,and the aerodynamic performance is improved ***,the effects of sweep angle and Reynolds number on the aerodynamic characteristics of flexible wing are also presented.